Wing for generating lift from an incident flow
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
B64C-009/00
B64C-021/10
B64C-003/38
A63H-027/00
B64C-003/10
B64C-023/00
B64C-033/02
F01D-005/12
출원번호
US-0640976
(2011-04-14)
등록번호
US-8973874
(2015-03-10)
우선권정보
NL-2004555 (2010-04-15)
국제출원번호
PCT/NL2011/050253
(2011-04-14)
§371/§102 date
20121210
(20121210)
국제공개번호
WO2011/129696
(2011-10-20)
발명자
/ 주소
Musters, Robert Jan
출원인 / 주소
B.V. Green X
대리인 / 주소
Thomas|Horstemeyer, LLP
인용정보
피인용 횟수 :
0인용 특허 :
2
초록▼
The invention relates to a wing for generating lift and comprises a trailing edge, a leading edge, an inner end, an outer end, a top surface and a bottom surface. The wing comprises an aerofoil with a chord line and a span direction. The leading edge comprises a kink between the inner end and the ou
The invention relates to a wing for generating lift and comprises a trailing edge, a leading edge, an inner end, an outer end, a top surface and a bottom surface. The wing comprises an aerofoil with a chord line and a span direction. The leading edge comprises a kink between the inner end and the outer end. The leading edge comprises a forward sweep part between the inner end and the kink extending towards the kink presenting an angle relative to the span direction. The leading edge comprises a backward sweep part between the kink and the outer end extending from the kink presenting an angle relative to the span direction. The top surface comprises a flow control means for controlling the lift at least partly located between a leading edge part between the kink and the outer end and located between the leading edge and the trailing edge.
대표청구항▼
1. A wing for generating lift from an incident flow comprising; a trailing edge, a leading edge, an inner end, an outer end, a top surface corresponding with a suction side and a bottom surface corresponding with a pressure side;in cross section, an aerofoil with a chord line which is defined by a s
1. A wing for generating lift from an incident flow comprising; a trailing edge, a leading edge, an inner end, an outer end, a top surface corresponding with a suction side and a bottom surface corresponding with a pressure side;in cross section, an aerofoil with a chord line which is defined by a straight line between the leading edge and the trailing edge of the aerofoil;a span direction that extends from the inner end towards the outer end which is perpendicular to the chord line;wherein the leading edge further comprises;a kink between the inner end and the outer end configured to generate a kink vortex to provide an additional lifting force in which the incident flow reaching the kink in the leading edge generates the kink vortex which travels over the top surface towards the trailing edge;a forward sweep part between the inner end and the kink extending towards the kink, wherein the forward sweep part presents a forward angle relative to the span direction between 5° and 40°;a backward sweep part between the kink and the outer end extending from the kink, wherein the backward sweep part presents a backward angle relative to the span direction between −5° and −40°;wherein the top surface comprises a flow control means for controlling the lift wherein the flow control means is at least partly located between a leading edge part between the kink and the outer end and located between the leading edge and the trailing edge, wherein the flow control means is positioned in the generated kink vortex to disturb the additional lifting force provided by the kink vortex. 2. A wing according to claim 1, wherein an angle of the kink is smaller than 180° . 3. A wing according to claim 1, wherein the kink is located on substantially one third of a straight line between the inner end and the outer end wherein the straight line is parallel to the span direction. 4. A wing according to claim 1, wherein the flow control means is fully located behind the leading edge part between the kink and the outer end. 5. A wing according to claim 1, wherein the flow control means is located between the leading edge and a reference line halfway the leading edge and the trailing edge. 6. A wing according to claim 1, wherein the flow control means comprises a hinged surface. 7. A wing according to claim 6, wherein the hinged surface is less than one fifth of the top surface. 8. A wing according to claim 6, wherein the hinged surface covers more than one tenth of the top surface. 9. A wing according to claim 1, wherein at the inner end the aerofoil is cambered and at the outer end the aerofoil is half symmetrical. 10. An aerial vehicle, comprising at least one wing according to claim 1, wherein the aerial vehicle further comprises; a frame, in which the wing has a free tip end and a root end which is rotatably fixed to the frame;a flapping mechanism for flapping the at least one wing with respect to the frame, in which the flapping mechanism allows a first movement of the wing which is a repeating upwards and downwards movement of the tip end while the root end is rotatably fixed to the frame, such that the wing rotates around an axis that is parallel to a chord line near the root end, in which the flapping mechanism allows a second movement of the wing which is a repeating positive and negative rotation around an axis parallel to the span direction, in which the flapping mechanism allows a third movement which is a repeating inward and outward displacement of the tip end with respect to the root end. 11. An aerial vehicle according to claim 10, wherein the wing further comprises a flow control actuator arranged between the top surface and the bottom surface. 12. A blade for a rotary wing, comprising at least one wing according to claim 1, wherein the flow control means comprises an air hole for disturbing the flow. 13. A wing according to claim 5, wherein the flow control means comprises a hinged surface. 14. A wing according to claim 13, wherein the hinged surface is less than one fifth of the top surface. 15. A wing according to claim 1, the flow control means is fully located behind the leading edge part between the kink and the outer end; andthe flow control means comprises a hinged surface. 16. A wing according to claim 1, wherein at the inner end the aerofoil is cambered and at the outer end the aerofoil is half symmetrical.
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이 특허에 인용된 특허 (2)
Russell ; Jr. William F. (Westport CT) Roncz John (Elkhart IN), Spoiler system for ground effect vehicles.
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